EP3257754A1 - Blitzschlagverteilung flugzeugverbundstrukturen - Google Patents

Blitzschlagverteilung flugzeugverbundstrukturen Download PDF

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Publication number
EP3257754A1
EP3257754A1 EP17176469.9A EP17176469A EP3257754A1 EP 3257754 A1 EP3257754 A1 EP 3257754A1 EP 17176469 A EP17176469 A EP 17176469A EP 3257754 A1 EP3257754 A1 EP 3257754A1
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EP
European Patent Office
Prior art keywords
metal
stud
metal sheet
composite component
metal stud
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP17176469.9A
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English (en)
French (fr)
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EP3257754B1 (de
Inventor
Ryan Schmidt
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Goodrich Corp
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Goodrich Corp
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B64D45/02—Lightning protectors; Static dischargers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
    • B29C70/86—Incorporated in coherent impregnated reinforcing layers, e.g. by winding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/88—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
    • B29C70/882—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced partly or totally electrically conductive, e.g. for EMI shielding
    • B29C70/885—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced partly or totally electrically conductive, e.g. for EMI shielding with incorporated metallic wires, nets, films or plates
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/14—Layered products comprising a layer of metal next to a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
    • B32B3/266—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/14—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers
    • B32B37/144—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers using layers with different mechanical or chemical conditions or properties, e.g. layers with different thermal shrinkage, layers under tension during bonding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/14—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers
    • B32B37/15—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with at least one layer being manufactured and immediately laminated before reaching its stable state, e.g. in which a layer is extruded and laminated while in semi-molten state
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B32B38/0012—Mechanical treatment, e.g. roughening, deforming, stretching
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • B32B5/028—Net structure, e.g. spaced apart filaments bonded at the crossing points
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
    • B32B7/02—Physical, chemical or physicochemical properties
    • B32B7/025—Electric or magnetic properties
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/103—Metal fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/20—Properties of the layers or laminate having particular electrical or magnetic properties, e.g. piezoelectric
    • B32B2307/202—Conductive
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/20—Properties of the layers or laminate having particular electrical or magnetic properties, e.g. piezoelectric
    • B32B2307/206—Insulating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2311/00—Metals, their alloys or their compounds
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2571/00—Protective equipment
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2605/00—Vehicles
    • B32B2605/18—Aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D25/00—Emergency apparatus or devices, not otherwise provided for
    • B64D25/08—Ejecting or escaping means
    • B64D25/14—Inflatable escape chutes
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Definitions

  • the present disclosure relates to systems and methods for lightning strike dispersion, and more specifically, to transferring electricity received by an aircraft from a lightning strike.
  • Certain components of an aircraft are often constructed from composite materials.
  • Such composite elements are often electrically nonconductive and thus prevent or at least hinder the transfer of electricity to a main electrical ground of an aircraft in the event of a lightning strike or other similar event. Further, because the composite elements are electrically nonconductive, a lightning strike could damage the composite element and/or the contents of the composite element, thus adversely affecting the performance and safety of the aircraft.
  • a lightning strike dispersion structure may include a composite component having an outboard surface, wherein the composite component is electrically nonconductive.
  • the lightning strike dispersion structure may include a metal sheet coupled to and extending across a minority portion of the outboard surface of the composite component, wherein the metal sheet is electrically conductive.
  • the lightning strike dispersion structure may also include a metal stud coupled to and in electrical contact with the metal sheet, the metal stud extending completely through the composite component, wherein the metal stud is electrically conductive.
  • the lightning strike dispersion structure may also include a metal mesh coupled to and extending across a majority portion of the outboard surface of the composite component, wherein the metal mesh is electrically conductive and the majority portion of the outboard surface of the composite component is inclusive of the minority portion of the outboard surface of the composite component such that the metal mesh extends across and is in electrical contact with the metal sheet.
  • the metal mesh may be in direct physical contact with the metal sheet.
  • the majority portion of the outboard surface of the composite component may have a surface area that is at least 10 times larger than a surface area of the minority portion of the outboard surface of the composite component.
  • the metal mesh is embedded in an exterior surface material of an aircraft.
  • the minority portion of the outboard surface of the composite component has a surface area that is at least 2 times larger than a cross-sectional area of a head of the metal stud.
  • the metal stud when coupled to the metal sheet, may be non-rotatable about a longitudinal axis of the metal stud.
  • the metal stud may be a self-clinching stud that is coupled to the metal sheet.
  • a head of the metal stud is flush with a surface of the metal sheet.
  • the metal stud may be permanently integrated with the composite component.
  • a longitudinal axis of the metal stud extends perpendicular to plies of the composite component.
  • the metal stud may be non-structural and thus may be free of a structural load.
  • the minority portion of the outboard surface of the composite component may have a surface area that is about 6.45 cm 2 (1 square inch).
  • a packboard of an aircraft may include a composite housing having an inboard surface and an outboard surface, wherein the composite housing is electrically nonconductive.
  • the packboard may also include a metal sheet coupled to and extending across a minority portion of the outboard surface of the composite housing, wherein the metal sheet is electrically conductive.
  • the packboard may also include a metal stud comprising a head and a tip longitudinally opposite the head.
  • the metal stud may be electrically conductive and may extend through the composite housing.
  • the head of the metal stud may be coupled to and in electrical contact with the metal sheet and the tip of the metal stud may protrude from the inboard surface of the composite housing. Further, the tip of the metal stud may be configured to be electrically connected to an electrical ground of the aircraft.
  • the packboard further includes a metal mesh coupled to and extending across a majority portion of the outboard surface of the composite housing, wherein the metal mesh is electrically conductive and the majority portion of the outboard surface of the composite housing is inclusive of the minority portion of the outboard surface of the composite housing such that the metal mesh extends across and is in electrical contact with the metal sheet.
  • at least the tip of the metal stud may be threaded and may be configured to couple with a threaded nut for electrically connecting the metal stud to the electrical ground of the aircraft.
  • the metal stud may be permanently integrated with the composite housing.
  • a method of manufacturing a packboard may include coupling a head of a metal stud that is electrically conductive to a metal sheet that is electrically conductive such that the metal stud is in electrical contact with the metal sheet and the head of the metal stud is substantially flush with a first surface of the metal sheet.
  • the method may also include laying plies of electrically nonconductive material across a second surface, opposite the first surface, of the metal sheet. Laying the plies may include molding the plies to shape a packboard housing form having an inboard surface and an outboard surface, the second surface of the metal sheet extending across a minority portion of the outboard surface of the packboard housing form.
  • Laying the plies may also include extending the metal stud completely through the plies and coupling a metal mesh that is electrically conductive across the first surface of the metal sheet and across a majority portion of the outboard surface of the packboard housing form, wherein the metal mesh is in electrical contact with the first surface of the metal sheet.
  • the method may further include curing the plies to set the packboard housing form.
  • coupling the head of the metal stud to the metal sheet occurs before laying the plies and before curing the plies.
  • a longitudinal axis of the metal stud is maintained perpendicular to the plies while laying the plies.
  • any of the method or process descriptions may be executed in any order and are not necessarily limited to the order presented.
  • any reference to singular includes plural embodiments, and any reference to more than one component or step may include a singular embodiment or step.
  • any reference to tacked, attached, fixed, coupled, connected or the like may include permanent, removable, temporary, partial, full and/or any other possible attachment option.
  • any reference to without contact (or similar phrases) may also include reduced contact or minimal contact.
  • Surface shading lines may be used throughout the figures to denote different parts but not necessarily to denote the same or different materials. Different cross-hatching is used throughout the figures to denote different parts but not necessarily to denote the same or different materials.
  • FIG. 1 illustrates a perspective view of an aircraft 5 having an exterior mounted composite component 10, in accordance with various embodiments.
  • Aircraft 5 may include a fuselage with wings fixed to the fuselage.
  • An emergency exit door 6 may be disposed on the fuselage to allow passengers to exit the aircraft 5.
  • the emergency exit door 6 in various embodiments, may be situated over the wings of the aircraft 5 such that passengers exiting through the emergency exit door 6 can exit onto the wing(s).
  • the exterior mounted composite component 10 may be, for example, a packboard 100 (with brief reference to FIG. 2 ) configured to store an evacuation slide assembly.
  • the composite component 10 maybe a panel or other exterior mounted composite structure of the aircraft 5.
  • composite component 10 refers to an electrically nonconductive structure. Electrically nonconductive elements disposed on or near the exterior of the aircraft 5 may present performance or safety liabilities in the event of a lightning strike. Accordingly, the present disclosure relates to transferring electricity from the exterior of the aircraft 5, through the electrically nonconductive composite component 10, and to the main electrical ground of the aircraft 5.
  • composite refers to layers or fibers set in a resin matrix.
  • composite may refer to carbon fibers, glass fibers, aramid fibers, and/or plastic fibers, among others, held together and set in a resin or epoxy matrix.
  • a lightning strike dispersion structure 105 for a packboard 100 is disclosed.
  • the lightning strike dispersion structure 105 includes various components, described below in greater detail, that facilitate the transfer of electricity through the packboard 100 to the main electrical ground of the aircraft 5.
  • the packboard 100 may be a fuselage-mounted container within which, for example, an evacuation slide assembly is housed.
  • the packboard 100 generally defines a chamber 116 for storing and/or housing one or more items or assemblies.
  • an access panel may extend across the opening of the chamber 116 to retain the contents of the packboard 100.
  • an evacuation slide assembly may jettison the access panel and deploy the inflatable evacuation slide in response to the emergency exit door 6 opening.
  • the lightning strike dispersion structure 105 for the packboard 100 includes a composite housing 110, a metal sheet 120 (with reference to FIG. 4 ), a metal mesh 130 (with reference to FIG. 4 ), and a metal stud 150 (with reference to FIG. 4 ). These components are described in greater detail below.
  • the terms "composite component 10," "packboard 100,” and “composite housing 110" refer to electrically nonconductive material. That is, the term “packboard 100" specifically refers to one type of “composite component 10" and the term “composite housing 110" specifically refers to the structural body that forms and defines the chamber 116 of the packboard 100.
  • the lightning strike dispersion subject matter of the present disclosure may be applied and implemented with other, non-packboard-type composite components 10.
  • the metal sheet 120, the metal mesh 130, and the metal stud 150 may be made from electrically conductive metal materials.
  • the metal sheet 120, the metal mesh 130, and the metal stud 150 may be made from aluminum, steel, copper, nickel, tin, brass, tungsten, or iron, among others, or alloys thereof.
  • the metal sheet 120, the metal mesh 130, and the metal stud 150 may be the same material or they may be different.
  • the packboard 100 has an inboard surface 112 (with reference to FIG. 3 ) and an outboard surface 114.
  • the term "outboard surface 114" refers to surfaces of the packboard 100 that are disposed exterior to the aircraft 5 while the term “inboard surface” refers to surfaces of the composite component 10 that are not disposed exterior to the aircraft.
  • the inboard surface 112 refers to surfaces that are disposed and/or face inward relative to the exterior skin of the aircraft.
  • the metal stud 150 extends through the composite housing 110 of the packboard 100 from the outboard surface 114 to the inboard surface 112.
  • the metal stud 150 is electrically conductive.
  • FIG. 4 illustrates a cross-section view of the metal stud 150 extending through the composite housing 110. While FIG. 4 shows the composite housing 110 having two layers, in various embodiments the composite housing 110 may have more than two layers of composite material. In various embodiments, the metal stud 150 may include a head 152 and a tip 154.
  • the metal sheet 120 is disposed adjacent a portion of the outboard surface 114 of the composite housing 110.
  • the head 152 of the metal stud 150 may be directly coupled to the metal sheet 120.
  • the metal stud 150 may be a self-clinching fastener and the head 152 of the metal stud 150 may be mounted and/or fixed to the metal sheet 120 so as to be non-rotatable about a longitudinal axis of the metal stud 150.
  • the metal sheet 120 may be a ductile material that allows the head 152 of the metal stud 150 to be non-rotatably embedded in the metal sheet 120.
  • the head 152 of the metal stud 150 is substantially flush with an exterior facing surface of the metal sheet 120.
  • the metal stud 150 may be permanently integrated with the metal sheet 120 and/or the composite housing 110 during the manufacture of the packboard 100.
  • the metal stud 150 may be non-structural and thus may not support a structural load.
  • the packboard 100 may be mechanically and structurally coupled to the aircraft 5 via fasteners or weldments other than the metal stud 150.
  • the metal sheet 120 is electrically conductive and, according to various embodiments, may extend across a minority portion of the outboard surface 114 of the composite housing 110.
  • the term "minority portion” refers to the portion (e.g., part of a whole) of the outboard surface 114 of the composite housing 110 across which the metal sheet 120 is disposed and thus also refers to the areal dimensions of a surface of the metal sheet 120 extending parallel to the outboard surface 114.
  • the minority portion may be less than half the outboard surface 114 of the composite housing 110. In various embodiments, the minority portion may be between about 161 mm 2 and 4032 cm 2 (0.5 and 25 square inches).
  • the minority portion may be between about 6.45 cm 2 and 58 cm 2 (1 and 9 square inches). In various embodiments, the minority portion may be about 6.45 cm 2 (1 square inch). In various embodiments, the minority portion of the outboard surface 114 of the composite housing 110 has a surface area that is at least 2 times larger than a cross-sectional area of the head 152 of the metal stud.
  • the metal mesh 130 is electrically conductive and, according to various embodiments, extends across a majority portion of the outboard surface 114 of the composite housing 110.
  • the term "majority portion” refers to the portion (e.g., part of a whole) of the outboard surface 114 of the composite housing 110 across which the metal mesh 130 is disposed and thus also refers to the areal dimensions of a surface of the metal mesh 130 extending parallel to the outboard surface 114.
  • the majority portion is inclusive of the minority portion. That is, according to various embodiments, the metal mesh 130 overlaps the metal sheet 120 so that the metal mesh 130 is in electrical contact with the metal sheet 120. In various embodiments, the metal mesh 130 is in direct physical contact with the metal sheet 120.
  • the majority portion may be more than half of the outboard surface 114 of the composite housing 110 and thus the metal mesh 130 may extend across more than half of the exterior surface area of the composite housing 110.
  • the majority portion of the outboard surface 114 has a surface area that is at least 10 times larger than a surface area of the minority portion of the outboard surface 114.
  • the metal mesh 130 may extend across substantially the entire outboard surface 114 of the composite housing 110. In various embodiments, the metal mesh 130 may be coupled with and/or embedded into an outer coating, skin, or paint. In various embodiments, the metal mesh 130 may electrically connect with or may be continuous with a similar metal mesh that extends across the exterior surface of the aircraft 5 for lightning strike electricity dispersion. Thus, electricity from a lightning strike may conduct through the metal mesh 130, through the metal sheet 120, through the metal stud 150, and to the main electrical ground of the aircraft 5. Thus, the metal sheet 120 may facilitate electrical conduction between the metal stud 150 and the metal mesh 130. The metal sheet 120 may also provide a secure medium to which the metal stud 150 is non-rotatably affixed.
  • FIG. 6 illustrates a partial view of the inboard surface 112 of the composite housing 110. Extending from the inboard surface 112 of the composite housing 110 is the tip 154 of the metal stud 150. In various embodiments, the tip 154 of the metal stud 150 may be threaded and one or more threaded nuts 161, 162 may be threadably engaged on the metal stud 150.
  • the electrically conductive cable 166 may have a coupler 164 that engages the tip 154 of the metal stud 150 and the threaded nut(s) 161, 162 may secure the coupler 164 in place to maintain the electrical connection between the electrically conductive cable 166 and the metal stud 150.
  • a nut may retain the coupler 164 of the electrically conductive cable 166 between the nut and the inboard surface 112 of the composite housing 110.
  • the coupler 164 may be retained coupled to the metal stud 150 between one or more nuts.
  • FIG. 7 illustrates a schematic flow chart diagram of a method 790 for manufacturing the packboard 100, in accordance with various embodiments.
  • the method 790 may include coupling the head 152 of the metal stud 150 to the metal sheet 120 such that the metal stud 150 is in electrical contact with the metal sheet 120 and the head 152 of the metal stud 150 is substantially flush with a first surface of the metal sheet 120 (step 792).
  • the method 790 may further include laying plies of electrically nonconductive material across a second surface, opposite the first surface, of the metal sheet 120 (step 794).
  • laying the plies includes molding the plies to shape a packboard housing form having an inboard surface and an outboard surface.
  • the second surface of the metal sheet 120 may extend across a minority portion of the outboard surface of the packboard housing form.
  • Laying the plies may also include extending the metal stud 150 completely through the plies.
  • the method 790 further includes, according to various embodiments, coupling the metal mesh 130 across the first surface of the metal sheet 120 and across a majority portion of the outboard surface of the packboard housing form, wherein the metal mesh 130 is in electrical contact with the first surface of the metal sheet 120 (step 796).
  • the method 790 also includes curing the plies to set the packboard housing form (step 798).
  • coupling the head 152 of the metal stud 150 to the metal sheet 120 occurs before laying the plies (step 794) and before curing the plies (step 798).
  • extending the metal stud 150 completely through the plies occurs as the plies are being laid and before the plies are cured (step 798).
  • a longitudinal axis of the metal stud 150 is maintained perpendicular to the plies while laying the plies (step 794).
  • references to "various embodiments”, “one embodiment”, “an embodiment”, “an example embodiment”, etc. indicate that the embodiment described may include a particular feature, structure, or characteristic, but every embodiment may not necessarily include the particular feature, structure, or characteristic. Moreover, such phrases are not necessarily referring to the same embodiment. Further, when a particular feature, structure, or characteristic is described in connection with an embodiment, it is submitted that it is within the knowledge of one skilled in the art to affect such feature, structure, or characteristic in connection with other embodiments whether or not explicitly described. After reading the description, it will be apparent to one skilled in the relevant art(s) how to implement the disclosure in alternative embodiments.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Shielding Devices Or Components To Electric Or Magnetic Fields (AREA)
  • Laminated Bodies (AREA)
  • Elimination Of Static Electricity (AREA)
  • Casings For Electric Apparatus (AREA)
EP17176469.9A 2016-06-17 2017-06-16 Blitzschlagverteilung in flugzeugverbundstrukturen Active EP3257754B1 (de)

Applications Claiming Priority (1)

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US15/186,116 US10457411B2 (en) 2016-06-17 2016-06-17 Lightning strike dispersion for composite aircraft structures

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EP3257754A1 true EP3257754A1 (de) 2017-12-20
EP3257754B1 EP3257754B1 (de) 2020-05-06

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US (2) US10457411B2 (de)
EP (1) EP3257754B1 (de)
CN (1) CN107521653B (de)
BR (1) BR102017008640A2 (de)
CA (2) CA3232332A1 (de)

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US10457412B2 (en) * 2016-09-16 2019-10-29 Rosemount Aerospace Inc. Electrical isolation of angle of attack vane bearings
CN109605783A (zh) * 2018-12-10 2019-04-12 河北汉光重工有限责任公司 一种解决复合材料结构件导电连续性的方法
US11038334B2 (en) * 2019-01-14 2021-06-15 The Boeing Company Aircraft wing composite ribs having electrical grounding paths

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EP0518461A1 (de) * 1991-06-13 1992-12-16 Air Cruisers Company Aufblasbare Rutsche für Flugzeug
WO1998058840A1 (fr) * 1997-06-20 1998-12-30 Aerospatiale Matra Structure anti-etincelage, notamment pour aeronef
EP0976653A1 (de) * 1998-07-29 2000-02-02 Construcciones Aeronauticas, S.A. Blitzschutzeinrichtung für Flugzeug-Verbundwerkstoffstrukturen
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Publication number Publication date
CN107521653A (zh) 2017-12-29
US20190291891A1 (en) 2019-09-26
US20170361944A1 (en) 2017-12-21
CA2964402A1 (en) 2017-12-17
CN107521653B (zh) 2022-05-10
CA2964402C (en) 2024-04-23
US10457411B2 (en) 2019-10-29
BR102017008640A2 (pt) 2018-01-02
CA3232332A1 (en) 2017-12-17
EP3257754B1 (de) 2020-05-06
US10450087B2 (en) 2019-10-22

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